US3756545A - Aircraft load ejector - Google Patents

Aircraft load ejector Download PDF

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Publication number
US3756545A
US3756545A US00186952A US3756545DA US3756545A US 3756545 A US3756545 A US 3756545A US 00186952 A US00186952 A US 00186952A US 3756545D A US3756545D A US 3756545DA US 3756545 A US3756545 A US 3756545A
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US
United States
Prior art keywords
piston
distributor
cylinder
tubular
ejection
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
US00186952A
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English (en)
Inventor
P Coutin
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
R Alkan et Cie
Original Assignee
R Alkan et Cie
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by R Alkan et Cie filed Critical R Alkan et Cie
Application granted granted Critical
Publication of US3756545A publication Critical patent/US3756545A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D1/00—Dropping, ejecting, releasing or receiving articles, liquids, or the like, in flight
    • B64D1/02—Dropping, ejecting, or releasing articles
    • B64D1/04—Dropping, ejecting, or releasing articles the articles being explosive, e.g. bombs
    • B64D1/06—Bomb releasing; Bomb doors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42—AMMUNITION; BLASTING
    • F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B3/00—Blasting cartridges, i.e. case and explosive
    • F42B3/006—Explosive bolts; Explosive actuators

Definitions

  • the ejection piston whether single or telescopic, mounted in a cylinder of conventional type, is hollow and its inner cavity comprises a tubular distributor close at its outer end but provided adjacent this erid with lateral ports adapted to co-act with an inner surface of the piston end for causing its inner space and the rear end of the piston to communicate with the atmosphere when this tubular distributor emerges from the ejection piston at the end of an expansion stroke of the ejection piston whereas the same movement of the tubular distributor uncovers lateral ports formed at the rear end of the piston to cause the fluid pressure in the chamber formed between the piston and the tubular distributor to act against the lower end of the fluid-tight portion of the piston in its cylinder, in order to move the piston upwards.
  • the present invention relates in general to means for jettisoning a load, notably a bomb, from an aircraft, and has specific reference to an ejector device of this character which is retractable to reduce drag.
  • the ejection piston whether single or telescopic, mounted in a cylinder of conventional type, is hollow and its inner cavity comprises a tubular distributer close at its outer end but provided adjacent this end with lateral ports adapted to co-act with an inner surface of the piston end for causing its inner space and the rear end of the piston to communicate with the atmosphere when this tubular distributor emerges from the ejection piston at the end of an expansion stroke of the ejection piston whereas the same movement of the tubular distributor uncovers lateral ports formed at the rear end of the piston to cause the fluid pressure in the chamber formed between the piston and the tubular distributor to act against the lower end of the fluid-tight portion of the piston in its cylinder, in order to move the piston upwards.
  • FIG. 1 is an axial section showing a single-piston ejection device in the position preceding its operation
  • FIG. 2 is a similar view after the ejection piston has been expelled completely by the gas released during the combustion of a pyrotechnic charge during the release of a bomb;
  • FIG. 3 is a similar view showing the relative position of the elements after the tubular distributor has moved out from the piston;
  • FIG. 4 is a corresponding view showing the device after the return of the ejection piston to its retracted position
  • FIG. 5 illustrates in axial section an ejection device comprising a two-section telescopic piston in the position obtaining before its operation
  • FIG. 6 is a similar view after the expansion of the first telescopic element
  • FIG. 7 is a similar view after the complete expansion of the telescopic ejection piston
  • FIG. 8 is a corresponding view showing the device after the emergence of the internal tubular distributor
  • FIG. 9 is a corresponding view showing the device after the second telescopic element of the telescopic piston has resumed its internal position
  • FIG. 10 is a corresponding view showing the device after the telescopic piston has been retracted completely.
  • the reference numberal 1 designates very diagrammatically the bomb to be jettisoned which is attached to the aircraft through any conventional releasable means
  • 2 is the vertical cylinder body rigid with the aircraft structure, in which the ejection piston is slidably mounted.
  • this cylinder 2 comprises a pipe 3 for supplying thereto the gas released as a consequence of the combustion of a pyrotechnic charge (not shown) during the release of the bomb.
  • a ring 4 is screwed in the inner lower end of the aforesaid cylinder 2 for guiding the ejection piston while limiting its downward or outward stroke.
  • the ejection piston comprises a rear section 5 adapted to slide in fluid-tight relationship in the bore of cylinder 2 until it abuts against the bottom ring 41 in the fully expanded position.
  • the main body of the ejection piston as shown at 6 is adapted to slide through the ring 4 of which the inner diameter is somewhat smaller than that of said cylinder bore, whereby an annular chamber 7 of variable volume is formed between this cylinder 2 and the piston section 5.
  • the piston body 6 has formed through its wall a plurality of lateral ports 8 opening inwards into a cylindrical chamber 9 receiving the rear end of the hollow or tubular distributor open at the top.
  • This tubular distributor comprises in succession, from top to bottom, a first section 10 slidably mounted in fluid-tight relationship in said chamber 9, a peripheral groove 11, a section 12 sliding in chamber 9 and closing the lateral ports 8 in the position obtaining before the actuation of the ejector (FIG. 1), a main body 13, a stroke-limiting flange or collar 14 and an end portion 15 adapted to slide in an end ring 16 screwed in the outer end of the piston body 6.
  • This end portion 15 has formed through the lateral walls of the tubular distributor a plurality of ports 17 causing the inner chamber 18 of this distributor to communicate either with the inner annular chamber 19 of ejection piston 6 (as shown in FIGS. 1 and 2 or with the atmosphere (position of FIGS.
  • the reference numeral 20 designates a screw plug sealing the lower end of tubular distributor section 15 and it is obvious that by simply removing this plug 20 it is possible to clean the interior of the distributor and also to remove the ring 16 and the distributor proper (parts 10 to for subsequently cleaning the interior of the ejection piston 5, 6.
  • This plug is advantageously provided with a wider external head projecting laterally beneath the ejection piston 6.
  • FIGS. 5 to 10 of the drawings the only difference with the preceding form of embodiment lies in the use of a telescopic ejection piston comprising essentially two tubular elements or sections.
  • the outer element similar to the above-described piston assembly 5, 6 comprises a rear section 21 sliding in fluid-tight relationship in the cylinder 2, a main body 22 and a lower or outer section 23 having a reduced inner diameter.
  • the wall of said body 22 has radial ports 24 formed therein just beneath the rear section 21, said ports 24 opening into the inner cylindrical cavity of assembly 21, 22 in which the inner telescopic element is adapted to slide.
  • This assembly is again similar to the above-described piston assembly 5, 6 in that it comprises a rear section 25 adapted to slide in fluid-tight relationship in said assembly 21, 22 and a body 26 providing an annular cavity 27 between the two telescopic elements.
  • Ports 28 are also formed through the wall of said body 26 and open inwards into a cylindrical cavity 29 receiving the upper end of the tubular distributor consisting of a hollow piston comprising in succession from top to bottom a fluid-tight portion 30, a peripheral groove 31, a section 32 slidably engaged in said cylindrical cavity 29 so as to close or uncover said ports 28, a main body 33, an abutment flange 34 and an end portion 35 slidably fitted in a ring 36 screwed to the lower end of the inner telescopic element.
  • Ports 37 similar to ports 17, cause the inner chamber 38 of tubular distributor 30-35 to communicate either with the chamber 39 formed between the inner telescopic element and the tubular distributor, or with the atmosphere according as the tubular distributor is partially extracted from the inner telescopic element.
  • a screw plug 40 seals the lower end of the tubular distributor and it is clear that the elements 25 to 40 described above respectively correspond to elements 5 to 20 of the form of embodiment of FIGS. 1 to 4.
  • the lower part of ring 36 presents a flange which, in the retracted position of the inner telescopic element, abutes against a housing formed in the end portion 23 of the outer telescopic element.
  • the telescopic piston device affords a longer ejection stroke for a same axial dimension of the complete device and the latter can be cleaned and disassembled as easily as in the case of the first form of embodiment.
  • a retractable ejector device for jettisoning a load from an aircraft comprising a cylinder having an inlet port at one end and a restricted open end, at least one piston positioned in and spaced from said cylinder, having a hollow interior open at both ends of said piston, a head at its inner end portion, slidable in said cylinder and of a greater diameter than said cylinder restricted open end, a restriction in said hollow interior and at least one port through said inner end portion, a tubular distributor positioned in and spaced from said piston hollow interior, having a head at its inner end slideable in said piston, an exterior recess in said tubular distributor head, a flange at its other end portion of greater diameter than said piston restriction and ports below said flange opening into said distributor interior and means closing said distributor at its outer end whereby gas from said cylinder port will move said piston outwardly and then said distributor for engaging and jettisoning the load and return said distributor and piston into said cylinder.
  • said piston comprises a plurality of telescopic tubular elements with each inner element thereof having an upper section sliding in fluidtight relationship with its surrounding elements, each of said surrounding elements having at least one port therethrough beneath its upper section and positioned for being cleared by the upper section of its inner element whereby the complete retraction of the inner element permits the gas to press against the piston other end.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Actuator (AREA)
  • Jet Pumps And Other Pumps (AREA)
US00186952A 1970-11-17 1971-10-06 Aircraft load ejector Expired - Lifetime US3756545A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7041162A FR2119821B1 (enExample) 1970-11-17 1970-11-17

Publications (1)

Publication Number Publication Date
US3756545A true US3756545A (en) 1973-09-04

Family

ID=9064265

Family Applications (1)

Application Number Title Priority Date Filing Date
US00186952A Expired - Lifetime US3756545A (en) 1970-11-17 1971-10-06 Aircraft load ejector

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US (1) US3756545A (enExample)
FR (1) FR2119821B1 (enExample)
GB (1) GB1314490A (enExample)

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3871604A (en) * 1972-11-02 1975-03-18 Pierre Fernand Coutin Retractable jettisoning ejector for aircrafts
US4015507A (en) * 1976-03-25 1977-04-05 The United States Of America As Represented By The Secretary Of The Navy Ejection system
US4088287A (en) * 1976-03-09 1978-05-09 R. Alkan & Cie. Dual-purpose ejector for aircraft load jettisoning mechanism
FR2375571A1 (fr) * 1976-12-22 1978-07-21 Rafaut & Cie Dispositif d'ejection a piston retractable
WO1981003314A1 (en) * 1980-05-16 1981-11-26 Rockwell International Corp Controlled output force actuator
US4552327A (en) * 1983-09-19 1985-11-12 Western Gear Corporation Hydraulic ejector
FR2572490A1 (fr) * 1984-10-31 1986-05-02 Alkan R & Cie Connecteur de securite pour element separable ou largable avec dispositif de retraction automatique
US4608907A (en) * 1983-04-28 1986-09-02 Western Gear Corporation Rotary launcher and hydraulic ejector system
US4753151A (en) * 1986-06-27 1988-06-28 Lockheed Corporation Self-retracting ballistic actuator system
US5238209A (en) * 1991-06-18 1993-08-24 General Dynamics Corporation, Space Systems Division Arrangement for attach, quick disconnect and jettison of rocket booster from space vehicle core
US5395149A (en) * 1992-11-09 1995-03-07 Aerospatiale Societe Nationale Industrielle Device for holding an object onto a support and subsequently separating it therefrom in a controlled sequence
US6073886A (en) * 1998-08-20 2000-06-13 Mcdonnell Douglas Corporation Constant pressure area telescoping piston and method of using same
US20100193640A1 (en) * 2009-01-30 2010-08-05 The Boeing Company Method and apparatus for satellite orbital change using space debris
US20130047835A1 (en) * 2011-08-30 2013-02-28 Marvin Engineering Co., Inc. Aircraft store ejector system
US9505495B2 (en) 2011-08-30 2016-11-29 Marvin Engineering Co., Inc. Aircraft store ejector system
CN115303502A (zh) * 2022-10-08 2022-11-08 成都航天万欣科技有限公司 一种无人机气动弹射装置

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2408520A1 (fr) * 1977-11-10 1979-06-08 Dassault Avions Perfectionnements aux ejecteurs pour charges largables
GB8808712D0 (en) * 1988-04-13 2001-08-15 Ml Aviation Co Ltd Explosive release unit
FR2836705B1 (fr) * 2002-03-04 2006-08-18 Lacroix Soc E Verin comprenant une admission de fluide unique pour les largages d'une charge
CN103758814B (zh) * 2013-12-31 2015-11-25 中船重工中南装备有限责任公司 一种缓冲抛放气缸

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2931341A (en) * 1957-01-07 1960-04-05 North American Aviation Inc Store election piston with gas return
US3037805A (en) * 1957-08-22 1962-06-05 Geffner Ted Store supporting and ejecting assembly for aircraft
GB1005266A (en) * 1962-08-03 1965-09-22 Ml Aviation Co Ltd Improvements in jettison devices for use in aircraft

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2935971A (en) * 1958-01-09 1960-05-10 Albert M Stott Single cycle self retracting thruster
GB1088571A (en) * 1964-02-21 1967-10-25 Plessey Uk Ltd Improvements in or relating to combined ejector and release devices for aircraft stores

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2931341A (en) * 1957-01-07 1960-04-05 North American Aviation Inc Store election piston with gas return
US3037805A (en) * 1957-08-22 1962-06-05 Geffner Ted Store supporting and ejecting assembly for aircraft
GB1005266A (en) * 1962-08-03 1965-09-22 Ml Aviation Co Ltd Improvements in jettison devices for use in aircraft

Cited By (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3871604A (en) * 1972-11-02 1975-03-18 Pierre Fernand Coutin Retractable jettisoning ejector for aircrafts
US4088287A (en) * 1976-03-09 1978-05-09 R. Alkan & Cie. Dual-purpose ejector for aircraft load jettisoning mechanism
US4015507A (en) * 1976-03-25 1977-04-05 The United States Of America As Represented By The Secretary Of The Navy Ejection system
FR2375571A1 (fr) * 1976-12-22 1978-07-21 Rafaut & Cie Dispositif d'ejection a piston retractable
WO1981003314A1 (en) * 1980-05-16 1981-11-26 Rockwell International Corp Controlled output force actuator
US4399968A (en) * 1980-05-16 1983-08-23 Rockwell International Corporation Controlled output force actuator
US4608907A (en) * 1983-04-28 1986-09-02 Western Gear Corporation Rotary launcher and hydraulic ejector system
US4552327A (en) * 1983-09-19 1985-11-12 Western Gear Corporation Hydraulic ejector
FR2572490A1 (fr) * 1984-10-31 1986-05-02 Alkan R & Cie Connecteur de securite pour element separable ou largable avec dispositif de retraction automatique
EP0180521A1 (fr) * 1984-10-31 1986-05-07 R. ALKAN & Cie. Connecteur de sécurité pour élément séparable ou largable avec dispositif de rétraction automatique
US4753151A (en) * 1986-06-27 1988-06-28 Lockheed Corporation Self-retracting ballistic actuator system
US5238209A (en) * 1991-06-18 1993-08-24 General Dynamics Corporation, Space Systems Division Arrangement for attach, quick disconnect and jettison of rocket booster from space vehicle core
US5395149A (en) * 1992-11-09 1995-03-07 Aerospatiale Societe Nationale Industrielle Device for holding an object onto a support and subsequently separating it therefrom in a controlled sequence
US6073886A (en) * 1998-08-20 2000-06-13 Mcdonnell Douglas Corporation Constant pressure area telescoping piston and method of using same
US20100193640A1 (en) * 2009-01-30 2010-08-05 The Boeing Company Method and apparatus for satellite orbital change using space debris
US8052092B2 (en) * 2009-01-30 2011-11-08 The Boeing Company Method and apparatus for satellite orbital change using space debris
US9505495B2 (en) 2011-08-30 2016-11-29 Marvin Engineering Co., Inc. Aircraft store ejector system
US9090347B2 (en) * 2011-08-30 2015-07-28 Marvin Engineering Co., Inc. Aircraft store ejector system
US9376209B2 (en) 2011-08-30 2016-06-28 Marvin Engineering Co., Inc. Aircraft store ejector system
US20130047835A1 (en) * 2011-08-30 2013-02-28 Marvin Engineering Co., Inc. Aircraft store ejector system
US11059585B2 (en) 2011-08-30 2021-07-13 Marvin Engineering Co., Inc. Aircraft store ejector system
US11174026B2 (en) 2011-08-30 2021-11-16 Marvin Engineering Co., Inc. Aircraft store ejector system
US11427320B2 (en) 2011-08-30 2022-08-30 Marvin Engineering Co., Inc. Aircraft store ejector system
US11858634B2 (en) 2011-08-30 2024-01-02 Marvin Engineering Co., Inc. Aircraft store ejector system
US12497168B2 (en) 2011-08-30 2025-12-16 Marvin Engineering Company, Inc. Aircraft store ejector system
CN115303502A (zh) * 2022-10-08 2022-11-08 成都航天万欣科技有限公司 一种无人机气动弹射装置
CN115303502B (zh) * 2022-10-08 2023-03-21 成都航天万欣科技有限公司 一种无人机气动弹射装置

Also Published As

Publication number Publication date
GB1314490A (en) 1973-04-26
FR2119821B1 (enExample) 1973-12-28
FR2119821A1 (enExample) 1972-08-11

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